EP1939430A3 - Turbofan engine assembly and method of assembling same - Google Patents

Turbofan engine assembly and method of assembling same Download PDF

Info

Publication number
EP1939430A3
EP1939430A3 EP07123173A EP07123173A EP1939430A3 EP 1939430 A3 EP1939430 A3 EP 1939430A3 EP 07123173 A EP07123173 A EP 07123173A EP 07123173 A EP07123173 A EP 07123173A EP 1939430 A3 EP1939430 A3 EP 1939430A3
Authority
EP
European Patent Office
Prior art keywords
turbofan engine
engine assembly
coupled
rotor section
assembly
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07123173A
Other languages
German (de)
French (fr)
Other versions
EP1939430B1 (en
EP1939430A2 (en
Inventor
Jan Christopher Schilling
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP1939430A2 publication Critical patent/EP1939430A2/en
Publication of EP1939430A3 publication Critical patent/EP1939430A3/en
Application granted granted Critical
Publication of EP1939430B1 publication Critical patent/EP1939430B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/403—Transmission of power through the shape of the drive components
    • F05D2260/4031—Transmission of power through the shape of the drive components as in toothed gearing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49236—Fluid pump or compressor making
    • Y10T29/49245—Vane type or other rotary, e.g., fan

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Retarders (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A turbofan engine assembly (10) is provided. A turbofan engine assembly includes a core gas turbine engine (13) including a high-pressure compressor (14), a combustor (16) disposed downstream from the high-pressure compressor, and a high-pressure turbine (18) coupled to the high-pressure compressor using a shaft. A turbofan engine assembly (10) further includes counter-rotating booster compressor (22) coupled to the core gas turbine engine, and the counter-rotating booster compressor includes a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction. The turbofan engine assembly (10) further includes a single stage fan assembly (12) coupled to the first rotor section, and a drive shaft (31) coupled between the low-pressure turbine (20) and the fan assembly. A turbofan engine assembly (10) further includes a gearbox (100) coupled between the drive shaft and the second rotor section such that the low-pressure turbine drives the gearbox and such that the gearbox drives the second rotor section.
EP07123173A 2006-12-21 2007-12-13 Turbofan engine assembly and method of assembling same Expired - Fee Related EP1939430B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/614,585 US7716914B2 (en) 2006-12-21 2006-12-21 Turbofan engine assembly and method of assembling same

Publications (3)

Publication Number Publication Date
EP1939430A2 EP1939430A2 (en) 2008-07-02
EP1939430A3 true EP1939430A3 (en) 2010-01-20
EP1939430B1 EP1939430B1 (en) 2013-02-20

Family

ID=39171421

Family Applications (1)

Application Number Title Priority Date Filing Date
EP07123173A Expired - Fee Related EP1939430B1 (en) 2006-12-21 2007-12-13 Turbofan engine assembly and method of assembling same

Country Status (4)

Country Link
US (1) US7716914B2 (en)
EP (1) EP1939430B1 (en)
JP (1) JP5155648B2 (en)
CA (1) CA2613606C (en)

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US7490460B2 (en) * 2005-10-19 2009-02-17 General Electric Company Gas turbine engine assembly and methods of assembling same
US8128021B2 (en) 2008-06-02 2012-03-06 United Technologies Corporation Engine mount system for a turbofan gas turbine engine
US20140174056A1 (en) 2008-06-02 2014-06-26 United Technologies Corporation Gas turbine engine with low stage count low pressure turbine
GB0903935D0 (en) 2009-03-09 2009-04-22 Rolls Royce Plc Gas turbine engine
US8517672B2 (en) * 2010-02-23 2013-08-27 General Electric Company Epicyclic gearbox
EP2415966A1 (en) 2010-08-05 2012-02-08 Siemens Aktiengesellschaft Power train for a gas turbine
US8777793B2 (en) 2011-04-27 2014-07-15 United Technologies Corporation Fan drive planetary gear system integrated carrier and torque frame
US9239012B2 (en) 2011-06-08 2016-01-19 United Technologies Corporation Flexible support structure for a geared architecture gas turbine engine
US9631558B2 (en) 2012-01-03 2017-04-25 United Technologies Corporation Geared architecture for high speed and small volume fan drive turbine
US8834095B2 (en) * 2011-06-24 2014-09-16 United Technologies Corporation Integral bearing support and centering spring assembly for a gas turbine engine
US8667773B2 (en) 2011-06-28 2014-03-11 United Technologies Corporation Counter-rotating turbomachinery
US8943792B2 (en) 2011-06-29 2015-02-03 United Technologies Corporation Gas-driven propulsor with tip turbine fan
US8935913B2 (en) 2012-01-31 2015-01-20 United Technologies Corporation Geared turbofan gas turbine engine architecture
US8863491B2 (en) 2012-01-31 2014-10-21 United Technologies Corporation Gas turbine engine shaft bearing configuration
US9222417B2 (en) 2012-01-31 2015-12-29 United Technologies Corporation Geared turbofan gas turbine engine architecture
US9835052B2 (en) * 2012-01-31 2017-12-05 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US8402741B1 (en) * 2012-01-31 2013-03-26 United Technologies Corporation Gas turbine engine shaft bearing configuration
US8887487B2 (en) 2012-01-31 2014-11-18 United Technologies Corporation Geared turbofan gas turbine engine architecture
US9038366B2 (en) 2012-01-31 2015-05-26 United Technologies Corporation LPC flowpath shape with gas turbine engine shaft bearing configuration
US10400629B2 (en) 2012-01-31 2019-09-03 United Technologies Corporation Gas turbine engine shaft bearing configuration
US20150345426A1 (en) 2012-01-31 2015-12-03 United Technologies Corporation Geared turbofan gas turbine engine architecture
US10145266B2 (en) 2012-01-31 2018-12-04 United Technologies Corporation Gas turbine engine shaft bearing arrangement
US10287914B2 (en) * 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
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US9850821B2 (en) 2012-02-28 2017-12-26 United Technologies Corporation Gas turbine engine with fan-tied inducer section
US9103227B2 (en) * 2012-02-28 2015-08-11 United Technologies Corporation Gas turbine engine with fan-tied inducer section
US8915700B2 (en) * 2012-02-29 2014-12-23 United Technologies Corporation Gas turbine engine with fan-tied inducer section and multiple low pressure turbine sections
US9194290B2 (en) 2012-02-29 2015-11-24 United Technologies Corporation Counter-rotating low pressure turbine without turbine exhaust case
US9011076B2 (en) 2012-02-29 2015-04-21 United Technologies Corporation Counter-rotating low pressure turbine with gear system mounted to turbine exhaust case
US9022725B2 (en) 2012-02-29 2015-05-05 United Technologies Corporation Counter-rotating low pressure turbine with gear system mounted to turbine exhaust case
US9028200B2 (en) 2012-02-29 2015-05-12 United Technologies Corporation Counter rotating low pressure turbine with splitter gear system
US10018119B2 (en) * 2012-04-02 2018-07-10 United Technologies Corporation Geared architecture with inducer for gas turbine engine
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US8756908B2 (en) 2012-05-31 2014-06-24 United Technologies Corporation Fundamental gear system architecture
US20150308351A1 (en) 2012-05-31 2015-10-29 United Technologies Corporation Fundamental gear system architecture
US8572943B1 (en) 2012-05-31 2013-11-05 United Technologies Corporation Fundamental gear system architecture
US8607576B1 (en) * 2012-06-07 2013-12-17 United Technologies Corporation Single turbine driving dual compressors
US9228535B2 (en) 2012-07-24 2016-01-05 United Technologies Corporation Geared fan with inner counter rotating compressor
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US20140314541A1 (en) * 2012-09-26 2014-10-23 United Technologies Corporation Turbomachine thrust balancing system
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US10724479B2 (en) 2013-03-15 2020-07-28 United Technologies Corporation Thrust efficient turbofan engine
WO2014151176A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Turbofan engine main bearing arrangement
US9624827B2 (en) 2013-03-15 2017-04-18 United Technologies Corporation Thrust efficient turbofan engine
EP3004595B1 (en) * 2013-06-03 2020-09-02 United Technologies Corporation Turbofan engine bearing and gearbox arrangement
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WO2015130386A2 (en) * 2013-12-12 2015-09-03 United Technologies Corporation Turbomachinery with high relative velocity
DE102014210297A1 (en) * 2014-05-30 2015-12-03 Lufthansa Technik Ag Dismantling process for a gas turbine
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US10669946B2 (en) 2015-06-05 2020-06-02 Raytheon Technologies Corporation Geared architecture for a gas turbine engine
US9909451B2 (en) * 2015-07-09 2018-03-06 General Electric Company Bearing assembly for supporting a rotor shaft of a gas turbine engine
US10208676B2 (en) 2016-03-29 2019-02-19 General Electric Company Gas turbine engine dual sealing cylindrical variable bleed valve
CN106194497A (en) * 2016-06-21 2016-12-07 杨京生 Fixing shaft type, tubular gas turbine, the turbofan aero-jet engine of single combustion chamber structure
US10669947B2 (en) 2016-07-11 2020-06-02 Raytheon Technologies Corporation Geared gas turbine engine
EP3296552B1 (en) 2016-09-20 2019-06-05 Rolls-Royce Deutschland Ltd & Co KG Gas turbine engine with a geared turbofan arrangement
EP3296524B1 (en) * 2016-09-20 2019-02-27 Rolls-Royce Deutschland Ltd & Co KG Gas turbine engine with a geared turbofan arrangement
EP3296540B1 (en) 2016-09-20 2019-01-23 Rolls-Royce Deutschland Ltd & Co KG Gas turbine engine with a geared turbofan arrangement
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US10392970B2 (en) 2016-11-02 2019-08-27 General Electric Company Rotor shaft architectures for a gas turbine engine and methods of assembly thereof
US10801442B2 (en) * 2017-02-08 2020-10-13 General Electric Company Counter rotating turbine with reversing reduction gear assembly
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Also Published As

Publication number Publication date
US7716914B2 (en) 2010-05-18
JP2008157237A (en) 2008-07-10
US20080148707A1 (en) 2008-06-26
JP5155648B2 (en) 2013-03-06
EP1939430B1 (en) 2013-02-20
EP1939430A2 (en) 2008-07-02
CA2613606C (en) 2015-11-03
CA2613606A1 (en) 2008-06-21

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